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Applied Nonsingular Astrodynamics. Optimal Low-Thrust Orbit Transfer. Cambridge Aerospace Series Part No. 45

  • ID: 4559378
  • Book
  • 476 Pages
  • Cambridge University Press
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This essential book describes the mathematical formulations and subsequent computer simulations required to accurately project the trajectory of spacecraft and rockets in space, using the formalism of optimal control for minimum-time transfer in general elliptic orbit. The material will aid research students in aerospace engineering, as well as practitioners in the field of spaceflight dynamics, in developing simulation software to carry out trade studies useful in vehicle and mission design. It will teach readers to develop flight software for operational applications in autonomous mode, so to actually transfer space vehicles from one orbit to another. The practical, real-life applications discussed will give readers a clear understanding of the mathematics of orbit transfer, allow them to develop their own operational software to fly missions, and to use the contents as a research tool to carry out even more complex analyses.
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1. The fundamental classic analysis of Edelbaum, Sackett and Malchow, with additional detailed derivations and extensions;
2. The analysis of the six-element formulation;
3. Optimal low-thrust rendezvous using equinoctial orbit elements;
4. Optimal low-thrust transfer using variable bounded thrust;
5. Minimum-time low-thrust rendezvous and transfer using epoch mean longitude formulation;
6. Trajectory optimization using eccentric longitude formulation;
7. Low-thrust trajectory optimization based on epoch eccentric longitude formulation;
8. Mechanics of trajectory optimization using nonsingular variational equations in polar coordinates;
9. Trajectory optimization using nonsingular orbital elements and true longitude;
10. The treatment of the Earth oblateness effect in trajectory optimization in equinoctial coordinates;
11. Minimum-time constant acceleration orbit transfer with first-order oblateness effect;
12. The streamlined and complete set of the nonsingular J2-perturbed dynamic and adjoint equations for trajectory optimization in terms of eccentric longitude;
13. The inclusion of the higher order harmonics in the modeling of optimal low-thrust orbit transfer;
14. Analytic expansions of luni-solar gravity perturbations along rotating axes for trajectory optimization: part 1: the dynamic system;
15. Analytic expansions of luni-solar gravity perturbations along rotating axes for trajectory optimization: part 2: the multipliers system and simulations;
16. Fourth order expansions of the luni-solar gravity perturbations along rotating axes for trajectory optimization; Index.
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Jean Albert Kéchichian
Jean Albert Kéchichian is a retired Engineering Specialist from The Aerospace Corporation. His career has included senior level engineering positions at NASA's Jet Propulsion Laboratory and at Ford Aerospace. His main areas of contribution are in spaceflight guidance and navigation. He is a Fellow of The American Astronautical Society, and his work has regularly appeared in Acta Astronautica, the Journal of Guidance Control and Dynamics, the Journal of the Astronautical Sciences, and the Journal of Spacecraft and Rockets. He holds Degrees in Aeronautical and Mechanical Engineering from l'Université de Liège, University of California, Berkeley, and a Ph.D. in Aeronautics and Astronautics from Stanford University.
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